EP1149761A1 - Dispositif de réduction du bruit sur les ailes d'aéronefs - Google Patents

Dispositif de réduction du bruit sur les ailes d'aéronefs Download PDF

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Publication number
EP1149761A1
EP1149761A1 EP01109291A EP01109291A EP1149761A1 EP 1149761 A1 EP1149761 A1 EP 1149761A1 EP 01109291 A EP01109291 A EP 01109291A EP 01109291 A EP01109291 A EP 01109291A EP 1149761 A1 EP1149761 A1 EP 1149761A1
Authority
EP
European Patent Office
Prior art keywords
vortex generators
vortex
wing
flap
wings
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP01109291A
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German (de)
English (en)
Other versions
EP1149761B1 (fr
Inventor
Ingo Dr.Ing. Borchers
Roger Dipl.-Ing. Drobietz
Michael Dr.rer.nat. Grünewald
Kurt Dipl-Phys. Mau
Johann Dr.Ing. Reichenberger
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Airbus Operations GmbH
Original Assignee
Airbus Operations GmbH
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Airbus Operations GmbH filed Critical Airbus Operations GmbH
Publication of EP1149761A1 publication Critical patent/EP1149761A1/fr
Application granted granted Critical
Publication of EP1149761B1 publication Critical patent/EP1149761B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
    • B64C21/10—Influencing air flow over aircraft surfaces by affecting boundary layer flow using other surface properties, e.g. roughness
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C23/00—Influencing air flow over aircraft surfaces, not otherwise provided for
    • B64C23/06—Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C7/00—Structures or fairings not otherwise provided for
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/10—Drag reduction

Definitions

  • the invention relates to a device for reducing noise on the wings of aircraft, in particular, e.g. on high-lift flaps or slats
  • the noise of aircraft in flight is caused to a large extent by the Airflow on the outer contour of the aircraft.
  • This noise component has a special effect on landing approach disturbing from the environment because of extended high-lift flaps Additional sources of noise arise on the aircraft and the noise effect in addition low flight altitude occurs.
  • vortex generators are provided on the inner and / or outer profile end face of a footprint and in particular a flap, by which the vortex system created in flight is influenced, which consists of a relatively large one running along the gap between the wing and the footprints Vortex, the main vortex, is formed.
  • Vortex the main vortex
  • a large number of small vortices are formed by the vortex generators, which draw energy from the main vortex without reducing the effect of the footprint or the buoyancy effect of the high-lift flap too much.
  • the noise radiated into the far field which arises due to the interaction of the different vortex systems with the surface of the flap and the flap side surface, is lower than with the large-scale vortex system that is undisturbed without the vortex generators.
  • An advantage of the invention is that with a relatively low design effort significant noise reduction is achieved, It is particularly advantageous that the Vortex generators based on factors such as wing geometry, selected flight conditions can be adapted with little effort, so that there is a different application efficient noise reduction.
  • Another advantage of the invention is that the vortex generators according to the invention have little Have weight and otherwise hardly any negative effects on the performance of the Aircraft.
  • the vortex generators 1 according to the invention or the arrangement 1 according to the invention from Vortex generators are on one footprint, e.g. a high-lift flap 3 one Wing or a wing 5 arranged, for their more detailed determination in Figure 1 Cartesian coordinate system is specified with an x, y and z direction, the y direction defines the longitudinal direction of the wing. Flaps of all kinds come as storage spaces Wing of an aircraft, e.g. Spoilers, flaps, slats, rudders or ailerons.
  • the footprint shown in Figure 1 is an extendable landing flap 3, which extends at least in sections over the length of the wing 5. With such Flaps form a vortex in flight in the area of transition 7 from wing 5 the landing flap 3, typically as discontinuity or a change in curvature of the Outer contour or is formed as a gap. A vortex runs across the outer, i.e. the Fuselage 9 (not shown) remote end portion 10 or over the profile surface of the Landing flap 3. The same applies to the end surface close to the fuselage.
  • the end area 10 typically includes an upper 11a and a lower 11b side edge or Edge lines and an intermediate profile side surface 13, as in the Embodiment according to Figure 1 is provided (Fig. 3).
  • the end region 10 can also be used as Edge or end line 11 or be formed as a closing line of the flap.
  • the flap 3 depending on its current Extension position to a part of its wing depth in a cutout 15 of wing 5 located so that between the edge line 11 and, respectively, the edge lines 11a, 11b of the Landing flap 3 and one of these opposite side edge 17 of the cutout 15 of the Wing 5 gives a gap 19.
  • the vortex generators 1 are at the outer end region 10 arranged. You can also use the inner, i.e. facing the fuselage 9 End portion 10 of the flap 3 may be provided.
  • the attachment of vortex generators 1 must not only be provided for flaps, but can also generally Control surfaces, such as spoilers or rowing, can be used in an advantageous manner. This too have an outer and an inner end region 10, on which the vortex generators 1 must be provided. You can also on the rear edge of the respective control surface, respectively the rear edge of the main wing, and in particular at the two end edges of the Slats are acoustically effective.
  • the vortex generators 1 are preferably inside the side surface 13, that is between the upper 11a and lower 11b side edge attached. But you can also directly one of the side edges 11a, 11b or attached to both.
  • the vortex generators 1 extend at least over at least a section 21 of FIG Profile depth 20 or over several sections 21a, 21b, 21c. Section 21 and the Sections 21a, 21b, 21c extend at least over a fifth and preferably over Two thirds of the profile depth 20.
  • the vortex generators 1 are arranged as a plurality of elongate elements 31 educated. These can basically have any cross-sectional shape, e.g. one have a circular, oval or rectangular cross-section. The cross section can be constant or variable along their longitudinal direction, e.g. rejuvenating be trained.
  • the elongated elements 31 can be designed flexibly, so that the Vortex generators are brush-shaped. But you can also use rigid elements have, ie represent a comb-like structure, as in the embodiment of Figures 1 and 2 is shown.
  • Elongated elements 31 project generally at an angle to the longitudinal direction of FIG High lift flap 3 away from the end region 10. You can also do this in the y direction or the longitudinal direction of the high-lift flap 3 or perpendicular to the profile side surface 13 stand, provided that in the respective embodiment of the high-lift flap 3 such is provided.
  • Section 21 or section 21a, 21b, 21c are of a series of elongated ones Elements 31 or more rows of elongated elements 31 are formed. It can too a plurality of sections 21 and 21 a, 21b, 21c running side by side can be provided, these can in particular run parallel to one another.
  • the length of the elongated elements 31 can be in the range between 5 and 100 mm, wherein they are preferably in the range between 5 and 15 mm.
  • vortex generators 1 depends on essential of the geometry of the wing and the high-lift flap 3, which for the Aircraft relevant angles of attack and flap positions and speeds from time to time are the application due to the prevailing aerodynamic processes on the wing to adapt with methods according to the prior art.
  • the vortex to be influenced by means of the vortex generators 1 is used in flaps that - such as Spoilers - unlike the described flap 3 as a special form of High lift flaps, formed in a different way, but this also runs over one Side edge of the flap, so that the device according to the invention even in other types Flaps for the purpose of the invention on a transverse to the x or longitudinal direction of the Provide flap extending end area.
  • the Vortex generators according to the invention also in the other aforementioned areas to be ordered.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Toys (AREA)
  • Mobile Radio Communication Systems (AREA)
  • Noise Elimination (AREA)
EP01109291A 2000-04-25 2001-04-17 Dispositif de réduction du bruit sur les ailes d'aéronefs Expired - Lifetime EP1149761B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10020177 2000-04-25
DE10020177A DE10020177A1 (de) 2000-04-25 2000-04-25 Einrichtung zur Lärmminderung an Tragflügeln von Flugzeugen

Publications (2)

Publication Number Publication Date
EP1149761A1 true EP1149761A1 (fr) 2001-10-31
EP1149761B1 EP1149761B1 (fr) 2006-04-12

Family

ID=7639842

Family Applications (1)

Application Number Title Priority Date Filing Date
EP01109291A Expired - Lifetime EP1149761B1 (fr) 2000-04-25 2001-04-17 Dispositif de réduction du bruit sur les ailes d'aéronefs

Country Status (7)

Country Link
US (1) US6491260B2 (fr)
EP (1) EP1149761B1 (fr)
JP (1) JP2001354198A (fr)
AT (1) ATE323023T1 (fr)
CA (1) CA2344950C (fr)
DE (2) DE10020177A1 (fr)
ES (1) ES2261290T3 (fr)

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1314642A3 (fr) * 2001-11-24 2004-01-14 Airbus Deutschland GmbH Dispositif pour réduire le bruit produit par des volets de bord d'attaque d'un aéronef
WO2007068450A1 (fr) * 2005-12-13 2007-06-21 Airbus Deutschland Gmbh Gouverne de direction d’aeronef commercial
WO2007095931A2 (fr) * 2006-02-23 2007-08-30 Airbus Deutschland Gmbh Volet aerodynamique pour avion, dote d'un dispositif agissant sur les tourbillons créés par un volet
FR2930235A1 (fr) * 2008-04-21 2009-10-23 Airbus France Sas Mat de suspension pour turbomoteur.
EP1527992A3 (fr) * 2003-11-03 2011-03-16 Patria Aerostructures Oy Dispositif pour la génération de tourbillons
CN102562436A (zh) * 2010-12-16 2012-07-11 通用电气公司 用于风力机中的转子叶片的降噪器
WO2014049328A1 (fr) * 2012-09-25 2014-04-03 Messier-Dowty Limited Plaque et procédé de modification d'écoulement d'air
DE102018121395A1 (de) * 2018-09-03 2020-03-05 Airbus Defence and Space GmbH Endrippenanordnung für eine Auftriebshilfevorrichtung eines Luftfahrzeugs mit Lärmminderung
US11279469B2 (en) 2016-07-12 2022-03-22 The Aircraft Performance Company Gmbh Airplane wing
US11312481B2 (en) 2017-07-12 2022-04-26 The Aircraft Performance Company Gmbh Airplane wing
US11396368B2 (en) 2017-12-15 2022-07-26 The Aircraft Performance Company Gmbh Airplane wing
US11427307B2 (en) 2018-01-15 2022-08-30 The Aircraft Performance Company Gmbh Airplane wing

Families Citing this family (52)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6685143B1 (en) * 2003-01-03 2004-02-03 Orbital Research Inc. Aircraft and missile forebody flow control device and method of controlling flow
US20050127239A1 (en) * 2003-08-25 2005-06-16 Srivastava Varad N. Flying work station
US7014142B2 (en) * 2004-02-03 2006-03-21 The Boeing Company Low-drag rotor/wing flap
DK1886016T3 (en) * 2005-05-17 2017-06-19 Vestas Wind Sys As Pitch-controlled wind turbine blade with turbulence generating means, a wind turbine and its use
EP1948504B1 (fr) * 2005-11-15 2010-04-14 Airbus Operations GmbH Volet de freinage pour aeronef
JP5043455B2 (ja) * 2006-03-28 2012-10-10 キヤノン株式会社 画像形成装置、その制御方法、システム、プログラム及び記憶媒体
US20080217484A1 (en) * 2006-11-14 2008-09-11 Airbus Deutschland Gmbh Brake flap for an aircraft
US7918653B2 (en) * 2007-02-07 2011-04-05 General Electric Company Rotor blade trailing edge assemby and method of use
BRPI0701438B1 (pt) * 2007-04-13 2019-11-19 Embraer Empresa Brasileira De Aeronautica S A superfície de controle de aeronave em combinação em combinação com um selo aerodinâmico para redução do ruído gerado por superfícies de controle de aeronaves
US7753316B2 (en) * 2007-04-27 2010-07-13 The Boeing Company Deployable flap edge fence
JP5046115B2 (ja) * 2007-12-27 2012-10-10 独立行政法人 宇宙航空研究開発機構 舵面端騒音低減デバイス
DE102008027618A1 (de) 2008-06-10 2009-12-31 Airbus Deutschland Gmbh Vorrichtung zur Bildung von aerodynamischen Wirbeln sowie Stellklappe und Tragflügel mit einer Vorrichtung zur Bildung von aerodynamischen Wirbeln
ES2365884B1 (es) * 2008-12-16 2012-09-12 Airbus Operations, S.L. Superficies móviles de aeronaves con ranuras selladas.
JP2010228598A (ja) * 2009-03-27 2010-10-14 Japan Aerospace Exploration Agency 翼胴結合部騒音低減デバイス
US8870124B2 (en) * 2009-07-10 2014-10-28 Peter Ireland Application of elastomeric vortex generators
JP5286527B2 (ja) 2009-07-13 2013-09-11 三菱重工業株式会社 高揚力発生装置、翼および高揚力発生装置の騒音低減装置
US8038396B2 (en) * 2010-06-22 2011-10-18 General Electric Company Vortex generator assembly for use with a wind turbine rotor blade and method for assembling a wind turbine rotor blade
US20110268557A1 (en) * 2010-09-29 2011-11-03 General Electric Company System and method for attenuating the noise of airfoils
DE102010047643A1 (de) * 2010-10-06 2012-04-12 Airbus Operations Gmbh Vorrichtung und ein Verfahren zum Erhöhen des aerodynamischen Auftriebs an einem Flugzeug
US8523515B2 (en) * 2010-11-15 2013-09-03 General Electric Company Noise reducer for rotor blade in wind turbine
US9132909B1 (en) * 2011-03-11 2015-09-15 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Flap edge noise reduction fins
US9227719B2 (en) * 2011-03-11 2016-01-05 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Reactive orthotropic lattice diffuser for noise reduction
US9302761B2 (en) * 2011-03-30 2016-04-05 The Society Of Japanese Aerospace Companies High-lift device of flight vehicle
US8414261B2 (en) 2011-05-31 2013-04-09 General Electric Company Noise reducer for rotor blade in wind turbine
US8834127B2 (en) 2011-09-09 2014-09-16 General Electric Company Extension for rotor blade in wind turbine
US8770649B2 (en) 2011-10-29 2014-07-08 Alexander Praskovsky Device, assembly, and system for reducing aerodynamic drag
US8430638B2 (en) 2011-12-19 2013-04-30 General Electric Company Noise reducer for rotor blade in wind turbine
US8840451B2 (en) * 2012-01-24 2014-09-23 Honeywell International Inc. Cabin pressure outflow valve with simplified whistle eliminator
JP5956803B2 (ja) * 2012-03-29 2016-07-27 一般社団法人日本航空宇宙工業会 飛行体の高揚力装置
US9505485B2 (en) * 2012-05-08 2016-11-29 Lockheed Martin Corporation Vortex generation
GB2504744B (en) * 2012-08-08 2014-06-25 Eads Uk Ltd Aircraft wing with slat arrangement establishing laminar boundary layer flow
US20140072441A1 (en) * 2012-09-12 2014-03-13 Michael J. Asheim Load and noise mitigation system for wind turbine blades
BR102012032959A2 (pt) 2012-12-21 2015-03-17 Embraer Sa Dispositivo aerodinâmico de largura variável
US9494134B2 (en) 2013-11-20 2016-11-15 General Electric Company Noise reducing extension plate for rotor blade in wind turbine
US10180125B2 (en) 2015-04-20 2019-01-15 General Electric Company Airflow configuration for a wind turbine rotor blade
US10252792B2 (en) * 2015-04-21 2019-04-09 The United States Of America As Represented By The Administrator Of Nasa Flow disruption devices for the reduction of high lift system noise
EP3181895A1 (fr) * 2015-12-17 2017-06-21 LM WP Patent Holding A/S Système à plaque de séparation pour une pale de turbine éolienne dentelée
US10532805B2 (en) * 2016-09-20 2020-01-14 Gulfstream Aerospace Corporation Airfoil for an aircraft having reduced noise generation
US10465652B2 (en) 2017-01-26 2019-11-05 General Electric Company Vortex generators for wind turbine rotor blades having noise-reducing features
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WO2019113689A1 (fr) 2017-12-15 2019-06-20 Bombardier Inc. Dispositif d'atténuation de bruit pour réduire le bruit produit par une ouverture dans un revêtement d'aéronef
JP7272675B2 (ja) * 2018-01-08 2023-05-12 ユニバーシティ・オブ・ノートルダム 抗力を低減するための繊維
US10767623B2 (en) 2018-04-13 2020-09-08 General Electric Company Serrated noise reducer for a wind turbine rotor blade
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US10746157B2 (en) 2018-08-31 2020-08-18 General Electric Company Noise reducer for a wind turbine rotor blade having a cambered serration
WO2020124172A1 (fr) 2018-12-20 2020-06-25 Embraer S.A. Joints aérodynamiques pour réduire le bruit aérodynamique associé à des surfaces de commande d'hypersustention d'aéronef
CN110844050A (zh) * 2019-11-02 2020-02-28 南京理工大学 一种前缘缝翼缝内针状涡流发生器
EP4201809B1 (fr) 2021-12-22 2024-08-14 Adática Engineering S.L Procédé de fabrication d'un joint aérodynamique et produit ainsi obtenu
GB2615311A (en) * 2022-01-31 2023-08-09 Airbus Operations Ltd Aircraft wing with movable wing tip device
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GB2628523A (en) * 2022-11-16 2024-10-02 Airbus Operations Ltd Aircraft wing

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3710691A1 (de) * 1987-03-31 1988-10-13 Josef Kecur Oberflaechenbeschichtung fuer aerodynamisch wirksame teile
US5253828A (en) * 1992-07-17 1993-10-19 The Board Of Regents Of The University Of Oklahoma Concealable flap-actuated vortex generator
DE9419119U1 (de) * 1994-11-10 1995-06-29 Chatschatrian, Vagarschak, 93055 Regensburg Beschichtung für bewegliche Objekte
US5845877A (en) * 1993-06-10 1998-12-08 Lockheed Martin Corporation Sealing assembly for reducing gaps between movable control surfaces of an aircraft

Family Cites Families (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2925232A (en) 1957-06-05 1960-02-16 Boeing Co Airplane spoiler assembly
US3578264A (en) * 1968-07-09 1971-05-11 Battelle Development Corp Boundary layer control of flow separation and heat exchange
US3596854A (en) * 1969-06-09 1971-08-03 William R Haney Jr Vortex generator for airfoil structures
US3881669A (en) 1973-05-16 1975-05-06 Martin Lessen Method and apparatus for elimination of airfoil trailing vortices
US3997132A (en) 1974-12-11 1976-12-14 The Garrett Corporation Method and apparatus for controlling tip vortices
US4039161A (en) * 1975-10-16 1977-08-02 Mcdonnell Douglas Corporation Hidden vortex generators
GB2051706A (en) 1979-06-19 1981-01-21 British Aerospace Aircraft wings
GB8314656D0 (en) 1983-05-26 1983-06-29 Secr Defence Aircraft control
DE3521329A1 (de) * 1985-06-14 1986-12-18 Messerschmitt-Bölkow-Blohm GmbH, 8012 Ottobrunn Wirbelgeneratoren- und grenzschichtabweiseranordnung
US4739957A (en) 1986-05-08 1988-04-26 Advanced Aerodynamic Concepts, Inc. Strake fence flap
US4776535A (en) * 1986-12-29 1988-10-11 United Technologies Corporation Convoluted plate to reduce base drag
JPH0232000A (ja) * 1988-07-19 1990-02-01 Mitsubishi Heavy Ind Ltd 高揚力翼
US5058837A (en) 1989-04-07 1991-10-22 Wheeler Gary O Low drag vortex generators
JPH0478793A (ja) * 1990-07-19 1992-03-12 Mitsubishi Heavy Ind Ltd 航空機
US5749546A (en) * 1995-07-10 1998-05-12 The Boeing Company Method and apparatus for reducing airframe aerosound
US5788191A (en) 1995-08-18 1998-08-04 Sikorsky Aircraft Corporation Half-plow vortex generators for rotor blades for reducing blade-vortex interaction noise
US5772155A (en) * 1996-06-01 1998-06-30 Nowak; Dieter K. Aircraft wing flaps
US6042059A (en) 1997-02-20 2000-03-28 Continuum Dynamics, Inc. System and method of vortex wake control using vortex leveraging
DE19719922C1 (de) * 1997-05-13 1998-11-12 Daimler Benz Aerospace Airbus Einrichtung zur Beeinflussung einer Wurzelströmung
US6082679A (en) 1997-06-26 2000-07-04 The Boeing Company Active system for early destruction of trailing vortices
US5983944A (en) * 1998-03-20 1999-11-16 Niv; Shaul E. Apparatus for active fluid control
DE19909190C2 (de) 1999-03-03 2001-02-22 Deutsch Zentr Luft & Raumfahrt Flugzeug mit mindestens einem Wirbelgenerator je Tragflügel zum Reduzieren der Wirbelstärke der Flügelhauptwirbel
JP2001301696A (ja) * 2000-04-24 2001-10-31 Mitsubishi Heavy Ind Ltd 騒音低減構造

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3710691A1 (de) * 1987-03-31 1988-10-13 Josef Kecur Oberflaechenbeschichtung fuer aerodynamisch wirksame teile
US5253828A (en) * 1992-07-17 1993-10-19 The Board Of Regents Of The University Of Oklahoma Concealable flap-actuated vortex generator
US5845877A (en) * 1993-06-10 1998-12-08 Lockheed Martin Corporation Sealing assembly for reducing gaps between movable control surfaces of an aircraft
DE9419119U1 (de) * 1994-11-10 1995-06-29 Chatschatrian, Vagarschak, 93055 Regensburg Beschichtung für bewegliche Objekte

Cited By (21)

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Publication number Priority date Publication date Assignee Title
EP1314642A3 (fr) * 2001-11-24 2004-01-14 Airbus Deutschland GmbH Dispositif pour réduire le bruit produit par des volets de bord d'attaque d'un aéronef
EP1527992A3 (fr) * 2003-11-03 2011-03-16 Patria Aerostructures Oy Dispositif pour la génération de tourbillons
WO2007068450A1 (fr) * 2005-12-13 2007-06-21 Airbus Deutschland Gmbh Gouverne de direction d’aeronef commercial
US8061652B2 (en) 2005-12-13 2011-11-22 Airbus Deutschland Gmbh Rudder of a commercial aircraft
WO2007095931A2 (fr) * 2006-02-23 2007-08-30 Airbus Deutschland Gmbh Volet aerodynamique pour avion, dote d'un dispositif agissant sur les tourbillons créés par un volet
WO2007095931A3 (fr) * 2006-02-23 2007-11-01 Airbus Gmbh Volet aerodynamique pour avion, dote d'un dispositif agissant sur les tourbillons créés par un volet
US8096513B2 (en) 2006-02-23 2012-01-17 Airbus Operations Gmbh Aerodynamic flap of an aircraft having a device which influences the flap vortex
CN101454202B (zh) * 2006-02-23 2012-05-23 空中客车德国有限公司 具有影响襟翼紊流的装置的飞机的空气动力学襟翼
FR2930235A1 (fr) * 2008-04-21 2009-10-23 Airbus France Sas Mat de suspension pour turbomoteur.
US8146868B2 (en) 2008-04-21 2012-04-03 Airbus Operations Sas Pylon for suspending a turboengine
CN102562436A (zh) * 2010-12-16 2012-07-11 通用电气公司 用于风力机中的转子叶片的降噪器
CN102562436B (zh) * 2010-12-16 2015-12-09 通用电气公司 用于风力机中的转子叶片的降噪器
WO2014049328A1 (fr) * 2012-09-25 2014-04-03 Messier-Dowty Limited Plaque et procédé de modification d'écoulement d'air
US10286996B2 (en) 2012-09-25 2019-05-14 Safran Landing Systems Uk Ltd Airflow modification patch and method
US11279469B2 (en) 2016-07-12 2022-03-22 The Aircraft Performance Company Gmbh Airplane wing
US11312481B2 (en) 2017-07-12 2022-04-26 The Aircraft Performance Company Gmbh Airplane wing
US11396368B2 (en) 2017-12-15 2022-07-26 The Aircraft Performance Company Gmbh Airplane wing
US11427307B2 (en) 2018-01-15 2022-08-30 The Aircraft Performance Company Gmbh Airplane wing
DE102018121395A1 (de) * 2018-09-03 2020-03-05 Airbus Defence and Space GmbH Endrippenanordnung für eine Auftriebshilfevorrichtung eines Luftfahrzeugs mit Lärmminderung
DE102018121395B4 (de) * 2018-09-03 2021-06-17 Airbus Defence and Space GmbH Endrippenanordnung für eine Auftriebshilfevorrichtung eines Luftfahrzeugs mit Lärmminderung
US11358704B2 (en) 2018-09-03 2022-06-14 Airbus Defence and Space GmbH Noise reduced end rib assembly for a high-lift device of an aircraft

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JP2001354198A (ja) 2001-12-25
CA2344950A1 (fr) 2001-10-25
ES2261290T3 (es) 2006-11-16
CA2344950C (fr) 2008-04-15
DE10020177A1 (de) 2001-11-08
US20010032907A1 (en) 2001-10-25
DE50109473D1 (de) 2006-05-24
EP1149761B1 (fr) 2006-04-12
ATE323023T1 (de) 2006-04-15
US6491260B2 (en) 2002-12-10

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